US20090155061A1 - sectorized nozzle for a turbomachine - Google Patents
sectorized nozzle for a turbomachine Download PDFInfo
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- US20090155061A1 US20090155061A1 US12/330,630 US33063008A US2009155061A1 US 20090155061 A1 US20090155061 A1 US 20090155061A1 US 33063008 A US33063008 A US 33063008A US 2009155061 A1 US2009155061 A1 US 2009155061A1
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- Prior art keywords
- sector
- nozzle
- longitudinally
- rail
- sectorized
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a sectorized nozzle, in particular for a low-pressure turbine of an airplane turboprop or turbojet.
- a turbine of this type comprises stages, each of which comprises a turbine wheel and a stator nozzle, each nozzle being sectorized, i.e. being made up of a plurality of nozzle sectors that are disposed circumferentially end to end.
- Each nozzle sector has two annular platform sectors extending one inside the other and interconnected by substantially radial vanes.
- the outer platform has means for fastening to an outer casing of the turbine.
- the nozzle sector includes an annular rail sector for supporting elements made of abradable material, the rail being situated radially inside the inner platform of the nozzle and being connected to the inside surface of said platform.
- the abradable material elements co-operate with annular wipers carried by the rotor of the turbine so as to form labyrinth type seals.
- the nozzle sectors are separated from one another by small clearances in the circumferential direction so as to accommodate thermal expansions of their platforms when the turbine is in operation.
- Proposals have already been made to stiffen the nozzle with the help of axial bearing means formed on the sectors of the inner platform of the nozzle, the bearing means of one platform sector being designed to co-operate with corresponding means formed on the adjacent inner platform sectors in order to limit deformation of the nozzle in operation.
- each inner platform sector has longitudinally-extending edges that are cut to be substantially Z-shaped and that are complementary to the corresponding longitudinally-extending edges of adjacent inner platform sectors.
- Each Z-shaped longitudinally-extending edge of a platform sector comprises two end portions parallel to the longitudinal direction that are offset in the circumferential direction and that are connected to each other by a perpendicular margin for coming to bear axially against the corresponding margin of an adjacent platform sector while the turbine is in operation so as to limit the above-mentioned parasitic movements and deformations of the nozzle.
- each platform sector need to be machined so as to from the Z-shaped cutouts. This machining is a difficult operation that runs the risk of damaging the nozzle.
- the machining of these longitudinally-extending edges consists in particular in making a first cut to form a bearing margin and a second cut to connect said bearing margin to an upstream or downstream circumferential edge of the inner platform. These cuts are made close to the vanes of the nozzle, and the curved shape of the vanes can interfere to a greater or lesser extent with the machining operation.
- that technology is applicable only to nozzle inner platforms that are relatively plane and cannot be generalized to all types of nozzle or of nozzle sector.
- a particular object of the present invention is to provide a solution to the problems of the prior art that is simple, effective, and inexpensive.
- the invention provides a sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors placed end to end and each having two coaxial annular platform sectors interconnected by substantially radial vanes, and an annular rail sector for supporting elements of abradable material, the rail sector being radially inside the sector of the inner platform and being connected to said inner surface of the platform sector, each nozzle sector including, on the longitudinally-extending edges of the sector of the inner platform, means for mutual circumferential engagement that co-operate with corresponding means provided on an adjacent nozzle sector, wherein the longitudinally-extending edges of the inner platform sectors form V-shapes.
- the longitudinally-extending edges of the inner platform sectors are V-shaped instead of being Z-shaped. These longitudinally-extending edges are thus defined by two margins, compared with three in the prior art.
- the longitudinally-extending edges are thus simpler in shape, so machining them is simple and faster since it consists in making a single oblique cut in each longitudinally-extending edge of the platform sectors, as compared with two cuts in the prior art (a cut in the circumferential direction and a longitudinal cut).
- the inner platform sector of each nozzle sector has one longitudinally-extending V-shaped edge with an angle at the apex that is greater than 180° and an opposite longitudinally-extending edge with an angle at the apex that is less than 180°.
- the first longitudinally-extending edge of each platform sector may be of a shape that is complementary to the second longitudinally-extending edge thereof, and all of the inner platform sectors may be identical so as to simplify fabrication of the nozzle sectors and so as to be suitable for mutually engaging the longitudinally-extending edges of the inner platform sectors one in another when fastening the nozzle sectors to the turbine casing.
- each longitudinally-extending edge of each sector of the inner platform has an upstream portion that is substantially parallel to the axis of revolution of the nozzle and a downstream portion that is oblique relative to said axis.
- the oblique downstream portion of one of the longitudinally-extending edges of the inner platform sector may be substantially parallel to the downstream portion of the suction side of the vane adjacent to said longitudinal edge. The downstream portion of this longitudinally-extending edge thus follows in part the curvature of the vane situated close to said longitudinally-extending edge.
- the oblique downstream portion of one longitudinally-extending edge of the inner platform sector is substantially parallel to the oblique downstream portion of the other longitudinally-extending edge of said platform sector, such that the longitudinally-extending edges of the platform sectors are mutually complementary.
- the rail sector of each nozzle sector comprises, at one of its circumferential ends, means for bearing axially on the rail sector of an adjacent nozzle sector.
- the means bearing axially between the nozzle sectors are thus no longer formed on the inner platform sectors but are offset to the sectors of the rail for supporting the abradable elements, and this is most advantageous for the following reasons.
- the axial bearing means are situated radially inside the inner platform of the nozzle and their shapes and dimensions are not limited relative to those of the inner platform. These bearing means are carried by or are formed on the nozzle rail sectors, and they can be made integrally with said rail sectors by machining or casting, or they can be fittings that are fastened thereto.
- the present invention is not limited to one particular type of nozzle or nozzle sector.
- the rail sector has a section that is substantially L-shaped and comprises a substantially radial wall connected at its outer periphery to the inside surface of an inner platform sector and at its inner periphery to one end of a sector of a substantially cylindrical wall carrying elements of abradable material, the axial bearing means of said rail sector being carried by its radial wall.
- the bearing means may be formed on the upstream face of the radial wall of the rail sector. Under such circumstances, the axial bearing means oppose twisting deformation of the nozzle sectors due in particular to the aerodynamic forces applied to the vanes of said sectors in operation. In a variant, the bearing means are formed on the downstream face of the radial wall of the sector of the rail.
- each rail sector includes at least one lateral tab extending circumferentially towards an adjacent rail sector and including a face for bearing axially against said adjacent rail sector.
- This axial bearing face is substantially perpendicular to the axis of revolution of the nozzle, and it faces upstream or downstream.
- the invention also provides a low-pressure turbine for a turbomachine that includes at least one sectorized nozzle of the above-specified type, and it also provides a turbomachine, such as an airplane turboprop or turbojet, that includes at least one nozzle as described above.
- FIG. 1 is a diagrammatic half-view in axial section of a low pressure turbine of a turbomachine
- FIGS. 2 and 3 are diagrammatic perspective views of a nozzle sector of a turbine, in accordance with the art prior to the invention.
- FIGS. 4 and 5 are fragmentary diagrammatic views in perspective of a turbine nozzle sector of the invention.
- FIG. 1 shows a low pressure turbine 10 for a turbomachine, the turbine comprising four stages each having a nozzle 12 carried by an outer casing 16 of the turbine and a turbine wheel 18 situated downstream from the nozzle 12 .
- the wheels 18 comprise disks 20 assembled together in axial alignment by annular flanges 22 and carrying blades 24 that are substantially radial. These wheels 18 are connected to a turbine shaft (not shown) via a drive cone 26 that is fastened to the annular flanges 22 of the disks.
- Each nozzle 12 comprises two annular platforms 30 and 32 that are coaxial, constituting respectively an inner platform and an outer platform, and defining between them an annular gas flow passage through the turbine, and between which there extend stationary vanes 14 that are substantially radial.
- the outer platforms 32 of the nozzles are secured by suitable means to the outer casing 16 of the turbine.
- Each of the inner platforms 30 of the nozzles is connected to an annular rail 34 that supports annular elements 36 of abradable material.
- Each annular rail 34 is arranged radially inside the inner platform 30 of a nozzle and presents a section that is generally L-shaped.
- the rail 34 has a substantially radial annular wall 38 that is connected at its outer periphery to the inside surface of the inner platform 30 of the nozzle and at its inner periphery to an axial end of a cylindrical wall 40 that supports the abradable elements 36 .
- abradable elements 36 are arranged radially outside and facing outer annular wipers 42 carried by the retaining plates 28 .
- the wipers 42 are for rubbing against the elements 36 so as to form labyrinth seals, thereby limiting the passage of air in the axial direction through these seals.
- the nozzles 12 of the turbine are sectorized, each being made up of a plurality of sectors disposed circumferentially end to end along the longitudinal axis of the turbine.
- FIGS. 2 and 3 show a sector of a nozzle 12 made in accordance with the art prior to the present invention.
- This sector of a nozzle 12 comprises a sector of the inner platform 30 and a sector of the outer platform 32 , which sectors are interconnected by five vanes 14 .
- the longitudinally-extending edges of the sectors of the inner and outer platforms 30 and 32 present shapes that are complementary to the longitudinally-extending edges corresponding thereto of the adjacent platform sectors of the nozzle sectors so that the longitudinal edges engage circumferentially one in another when the nozzle is assembled.
- the longitudinally-extending edges 44 and 44 ′ of the inner platform 30 are machined to have a Z-shape so as to define axial bearing means between the sectors of the nozzle 12 .
- Each of the longitudinally-extending edges 44 , 44 ′ of the sectors of the inner platform 30 includes an axial bearing margin 46 (or 48 ) that extends substantially perpendicularly to the longitudinal axis of the turbine and that faces upstream (margin 46 )—or downstream (margin 48 )—and is designed to bear axially against a corresponding bearing margin facing downstream (margin 48 )—or upstream (margin 46 )—of an adjacent sector of the inner platform 30 .
- Each sector of the inner platform 30 includes at one of its lateral ends a bearing margin 46 facing upstream and at its other lateral end a bearing margin 48 facing downstream. The axial thrust of a sector of the inner platform 30 on an adjacent sector of the inner platform enables parasitic movements and vibration of the sectors of the nozzle 12 to be limited while the turbine is in operation.
- Each bearing margin 46 , 48 is connected at a first circumferential end to the downstream end of a longitudinally-extending margin 50 that extends to the upstream circumferential edge 54 of the sector of the platform 30 , substantially parallel to the longitudinal axis of the turbine.
- the second circumferential end of the bearing face 46 , 48 is connected to the upstream end of a second longitudinal margin 52 that is connected at its other end to the downstream circumferential edge 56 of the sector of the platform 30 .
- the margins 50 , 52 are parallel to each other and they are offset from each other in the circumferential direction by a distance equal to the circumferential size of the bearing margins 46 , 48 .
- Machining the longitudinally-extending edges of the sectors of the inner platform 30 presents numerous drawbacks as described above.
- the invention enables these problems to be remedied at least in part by simplifying the longitudinally-extending edges of the sectors of the inner platform 30 by making them V-shape.
- the inner platform sector 130 of each nozzle sector has a first longitudinally-extending edge 144 that is V-shaped with an angle at the apex that is greater than 180° ( FIG. 4 ), for example lying in the range 210° to 240°, and a second longitudinal edge 144 ′ that is V-shaped with its angle at the apex being less than 180° ( FIG. 5 ), for example lying in the range 120° to 150°.
- each inner platform sector 130 is complementary to its second longitudinally-extending edge 144 ′, and the sectors of the inner platform in all of the nozzle sectors are identical so that the longitudinally-extending edges 144 , 144 ′ of each platform sector 130 can engage in the corresponding longitudinally-extending edges of the adjacent platform sectors 130 .
- Each of the longitudinally-extending edges 144 , 144 ′ of each inner platform sector 130 has a first margin 150 or upstream end portion that extends in a longitudinal direction from the upstream circumferential edge 154 of the platform sector 130 to the connection between the radially extending wall 138 of the rail sector 134 and the platform sector 130 .
- Each longitudinally-extending edge 144 , 144 ′ has a second margin 166 or downstream end portion that extends obliquely relative to the longitudinal axis of the turbine, this second margin 166 directly connecting the downstream end of the first margin 150 to the downstream circumferentially-extending edge 156 of the inner platform sector 130 .
- the second margins 166 of the longitudinally-extending edges 144 , 144 ′ of the inner platform sector 130 are mutually parallel.
- the margin 166 of the longitudinally-extending edge 144 extends substantially parallel to and at a short distance from an end portion of the suction side of the vane 114 situated in the vicinity of said edge 144 ( FIG. 4 ), and the margin 166 of the other longitudinally-extending edge 144 ′ extends substantially parallel to and at a short distance from an end portion of the pressure side of the opposite vane 114 situated in the vicinity of said edge 144 ′ ( FIG. 4 ).
- the oblique margins 166 of the inner platform sectors 130 can bear against one another so as to limit the parasitic deformation and movements of the nozzle sectors in operation.
- the rail sector 134 of each nozzle sector 112 has at one of its circumferential ends a lateral tab 160 bearing axially against the rail sector of an adjacent nozzle sector.
- the tab 160 has an orientation that is substantially circumferential and includes a first circumferential end connected to the rail sector 134 , via its outer radial wall 138 .
- the second circumferential end of the tab 160 includes an axial bearing face 162 for co-operating with a corresponding face 164 of the outer radial wall 138 of the adjacent rail sector 134 , the faces 162 and 164 being substantially perpendicular to the longitudinal axis of the turbine.
- the tab 160 is situated downstream from the radial wall 138 of the rail sector 134 and is connected via its first end to a downstream face of said wall.
- the bearing face 162 of this tab faces upstream and is designed to bear against a downstream-facing face 164 of the radial wall 138 of the adjacent rail sector 134 .
- the tab 160 is situated upstream from the radial wall 138 of the rail sector and is connected via one end to an upstream face of said wall, the bearing face 162 of said tab facing downstream and co-operating with an upstream-facing face 164 of the radial wall of the adjacent rail sector 134 .
- each nozzle sector 112 may be made as a single casting or by machining with at least one lateral bearing tab 160 of the above-described type.
- the lateral tab 160 is a fitting and is fastened to one circumferential ends of each rail sector. Any type of nozzle sector may be fitted with this type of bearing tab.
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Abstract
Description
- The present invention relates to a sectorized nozzle, in particular for a low-pressure turbine of an airplane turboprop or turbojet.
- A turbine of this type comprises stages, each of which comprises a turbine wheel and a stator nozzle, each nozzle being sectorized, i.e. being made up of a plurality of nozzle sectors that are disposed circumferentially end to end.
- Each nozzle sector has two annular platform sectors extending one inside the other and interconnected by substantially radial vanes. The outer platform has means for fastening to an outer casing of the turbine. The nozzle sector includes an annular rail sector for supporting elements made of abradable material, the rail being situated radially inside the inner platform of the nozzle and being connected to the inside surface of said platform. The abradable material elements co-operate with annular wipers carried by the rotor of the turbine so as to form labyrinth type seals.
- The nozzle sectors are separated from one another by small clearances in the circumferential direction so as to accommodate thermal expansions of their platforms when the turbine is in operation.
- In operation they are subjected to vibration and to dynamic stresses that are relatively large and that can lead to small parasitic movements of the nozzle sectors and to deformations of these sectors, in particular in twisting.
- Proposals have already been made to stiffen the nozzle with the help of axial bearing means formed on the sectors of the inner platform of the nozzle, the bearing means of one platform sector being designed to co-operate with corresponding means formed on the adjacent inner platform sectors in order to limit deformation of the nozzle in operation.
- In the prior art, each inner platform sector has longitudinally-extending edges that are cut to be substantially Z-shaped and that are complementary to the corresponding longitudinally-extending edges of adjacent inner platform sectors. Each Z-shaped longitudinally-extending edge of a platform sector comprises two end portions parallel to the longitudinal direction that are offset in the circumferential direction and that are connected to each other by a perpendicular margin for coming to bear axially against the corresponding margin of an adjacent platform sector while the turbine is in operation so as to limit the above-mentioned parasitic movements and deformations of the nozzle.
- However, that technology presents drawbacks. The longitudinally-extending edges of each platform sector need to be machined so as to from the Z-shaped cutouts. This machining is a difficult operation that runs the risk of damaging the nozzle. The machining of these longitudinally-extending edges consists in particular in making a first cut to form a bearing margin and a second cut to connect said bearing margin to an upstream or downstream circumferential edge of the inner platform. These cuts are made close to the vanes of the nozzle, and the curved shape of the vanes can interfere to a greater or lesser extent with the machining operation. Finally, that technology is applicable only to nozzle inner platforms that are relatively plane and cannot be generalized to all types of nozzle or of nozzle sector.
- A particular object of the present invention is to provide a solution to the problems of the prior art that is simple, effective, and inexpensive.
- To this end, the invention provides a sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors placed end to end and each having two coaxial annular platform sectors interconnected by substantially radial vanes, and an annular rail sector for supporting elements of abradable material, the rail sector being radially inside the sector of the inner platform and being connected to said inner surface of the platform sector, each nozzle sector including, on the longitudinally-extending edges of the sector of the inner platform, means for mutual circumferential engagement that co-operate with corresponding means provided on an adjacent nozzle sector, wherein the longitudinally-extending edges of the inner platform sectors form V-shapes.
- According to the invention, the longitudinally-extending edges of the inner platform sectors are V-shaped instead of being Z-shaped. These longitudinally-extending edges are thus defined by two margins, compared with three in the prior art. The longitudinally-extending edges are thus simpler in shape, so machining them is simple and faster since it consists in making a single oblique cut in each longitudinally-extending edge of the platform sectors, as compared with two cuts in the prior art (a cut in the circumferential direction and a longitudinal cut).
- Preferably, the inner platform sector of each nozzle sector has one longitudinally-extending V-shaped edge with an angle at the apex that is greater than 180° and an opposite longitudinally-extending edge with an angle at the apex that is less than 180°. The first longitudinally-extending edge of each platform sector may be of a shape that is complementary to the second longitudinally-extending edge thereof, and all of the inner platform sectors may be identical so as to simplify fabrication of the nozzle sectors and so as to be suitable for mutually engaging the longitudinally-extending edges of the inner platform sectors one in another when fastening the nozzle sectors to the turbine casing.
- By way of example, each longitudinally-extending edge of each sector of the inner platform has an upstream portion that is substantially parallel to the axis of revolution of the nozzle and a downstream portion that is oblique relative to said axis. The oblique downstream portion of one of the longitudinally-extending edges of the inner platform sector may be substantially parallel to the downstream portion of the suction side of the vane adjacent to said longitudinal edge. The downstream portion of this longitudinally-extending edge thus follows in part the curvature of the vane situated close to said longitudinally-extending edge. There is no risk of the machining performed to make this downstream portion doing damage to the vane, since the cutter tool is further away from the vane and is moved in a direction that is parallel to the curvature thereof, so there is no risk of it coming into contact with the vane.
- The oblique downstream portion of one longitudinally-extending edge of the inner platform sector is substantially parallel to the oblique downstream portion of the other longitudinally-extending edge of said platform sector, such that the longitudinally-extending edges of the platform sectors are mutually complementary.
- According to another characteristic of the invention, the rail sector of each nozzle sector comprises, at one of its circumferential ends, means for bearing axially on the rail sector of an adjacent nozzle sector. The means bearing axially between the nozzle sectors are thus no longer formed on the inner platform sectors but are offset to the sectors of the rail for supporting the abradable elements, and this is most advantageous for the following reasons.
- The axial bearing means are situated radially inside the inner platform of the nozzle and their shapes and dimensions are not limited relative to those of the inner platform. These bearing means are carried by or are formed on the nozzle rail sectors, and they can be made integrally with said rail sectors by machining or casting, or they can be fittings that are fastened thereto.
- Furthermore, the present invention is not limited to one particular type of nozzle or nozzle sector.
- The rail sector has a section that is substantially L-shaped and comprises a substantially radial wall connected at its outer periphery to the inside surface of an inner platform sector and at its inner periphery to one end of a sector of a substantially cylindrical wall carrying elements of abradable material, the axial bearing means of said rail sector being carried by its radial wall.
- The bearing means may be formed on the upstream face of the radial wall of the rail sector. Under such circumstances, the axial bearing means oppose twisting deformation of the nozzle sectors due in particular to the aerodynamic forces applied to the vanes of said sectors in operation. In a variant, the bearing means are formed on the downstream face of the radial wall of the sector of the rail.
- According to another characteristic of the invention, each rail sector includes at least one lateral tab extending circumferentially towards an adjacent rail sector and including a face for bearing axially against said adjacent rail sector. This axial bearing face is substantially perpendicular to the axis of revolution of the nozzle, and it faces upstream or downstream.
- The invention also provides a low-pressure turbine for a turbomachine that includes at least one sectorized nozzle of the above-specified type, and it also provides a turbomachine, such as an airplane turboprop or turbojet, that includes at least one nozzle as described above.
- The invention can be better understood and other details, characteristics and advantages of the present invention appear more clearly on reading the following description made by way of non-limiting example and with reference to the accompanying drawings, in which:
-
FIG. 1 is a diagrammatic half-view in axial section of a low pressure turbine of a turbomachine; -
FIGS. 2 and 3 are diagrammatic perspective views of a nozzle sector of a turbine, in accordance with the art prior to the invention; and -
FIGS. 4 and 5 are fragmentary diagrammatic views in perspective of a turbine nozzle sector of the invention. - Reference is made initially to
FIG. 1 which shows alow pressure turbine 10 for a turbomachine, the turbine comprising four stages each having anozzle 12 carried by anouter casing 16 of the turbine and aturbine wheel 18 situated downstream from thenozzle 12. - The
wheels 18 comprisedisks 20 assembled together in axial alignment byannular flanges 22 and carryingblades 24 that are substantially radial. Thesewheels 18 are connected to a turbine shaft (not shown) via adrive cone 26 that is fastened to theannular flanges 22 of the disks. -
Annular retaining plates 28 for axially retaining theblades 24 on thedisks 20 and are mounted between the disks, with each having an innerradial wall 29 that is clamped axially between theannular flanges 22 of two adjacent disks. - Each
nozzle 12 comprises twoannular platforms stationary vanes 14 that are substantially radial. Theouter platforms 32 of the nozzles are secured by suitable means to theouter casing 16 of the turbine. - Each of the
inner platforms 30 of the nozzles is connected to anannular rail 34 that supportsannular elements 36 of abradable material. Eachannular rail 34 is arranged radially inside theinner platform 30 of a nozzle and presents a section that is generally L-shaped. Therail 34 has a substantially radialannular wall 38 that is connected at its outer periphery to the inside surface of theinner platform 30 of the nozzle and at its inner periphery to an axial end of acylindrical wall 40 that supports theabradable elements 36. - These
abradable elements 36 are arranged radially outside and facing outerannular wipers 42 carried by theretaining plates 28. Thewipers 42 are for rubbing against theelements 36 so as to form labyrinth seals, thereby limiting the passage of air in the axial direction through these seals. - The
nozzles 12 of the turbine are sectorized, each being made up of a plurality of sectors disposed circumferentially end to end along the longitudinal axis of the turbine. -
FIGS. 2 and 3 show a sector of anozzle 12 made in accordance with the art prior to the present invention. This sector of anozzle 12 comprises a sector of theinner platform 30 and a sector of theouter platform 32, which sectors are interconnected by fivevanes 14. - The longitudinally-extending edges of the sectors of the inner and
outer platforms - In the prior art, the longitudinally-extending
edges inner platform 30 are machined to have a Z-shape so as to define axial bearing means between the sectors of thenozzle 12. - Each of the longitudinally-extending
edges inner platform 30 includes an axial bearing margin 46 (or 48) that extends substantially perpendicularly to the longitudinal axis of the turbine and that faces upstream (margin 46)—or downstream (margin 48)—and is designed to bear axially against a corresponding bearing margin facing downstream (margin 48)—or upstream (margin 46)—of an adjacent sector of theinner platform 30. Each sector of theinner platform 30 includes at one of its lateral ends abearing margin 46 facing upstream and at its other lateral end abearing margin 48 facing downstream. The axial thrust of a sector of theinner platform 30 on an adjacent sector of the inner platform enables parasitic movements and vibration of the sectors of thenozzle 12 to be limited while the turbine is in operation. - Each bearing
margin margin 50 that extends to the upstreamcircumferential edge 54 of the sector of theplatform 30, substantially parallel to the longitudinal axis of the turbine. The second circumferential end of the bearingface longitudinal margin 52 that is connected at its other end to the downstreamcircumferential edge 56 of the sector of theplatform 30. Themargins margins - Machining the longitudinally-extending edges of the sectors of the
inner platform 30 presents numerous drawbacks as described above. The invention enables these problems to be remedied at least in part by simplifying the longitudinally-extending edges of the sectors of theinner platform 30 by making them V-shape. - In the embodiment of the invention shown in
FIGS. 4 and 5 , theinner platform sector 130 of each nozzle sector has a first longitudinally-extendingedge 144 that is V-shaped with an angle at the apex that is greater than 180° (FIG. 4 ), for example lying in the range 210° to 240°, and a secondlongitudinal edge 144′ that is V-shaped with its angle at the apex being less than 180° (FIG. 5 ), for example lying in the range 120° to 150°. - The first longitudinally-extending
edge 144 of eachinner platform sector 130 is complementary to its second longitudinally-extendingedge 144′, and the sectors of the inner platform in all of the nozzle sectors are identical so that the longitudinally-extendingedges platform sector 130 can engage in the corresponding longitudinally-extending edges of theadjacent platform sectors 130. - Each of the longitudinally-extending
edges inner platform sector 130 has afirst margin 150 or upstream end portion that extends in a longitudinal direction from the upstreamcircumferential edge 154 of theplatform sector 130 to the connection between theradially extending wall 138 of therail sector 134 and theplatform sector 130. Each longitudinally-extendingedge second margin 166 or downstream end portion that extends obliquely relative to the longitudinal axis of the turbine, thissecond margin 166 directly connecting the downstream end of thefirst margin 150 to the downstream circumferentially-extendingedge 156 of theinner platform sector 130. Thesecond margins 166 of the longitudinally-extendingedges inner platform sector 130 are mutually parallel. Themargin 166 of the longitudinally-extendingedge 144 extends substantially parallel to and at a short distance from an end portion of the suction side of thevane 114 situated in the vicinity of said edge 144 (FIG. 4 ), and themargin 166 of the other longitudinally-extendingedge 144′ extends substantially parallel to and at a short distance from an end portion of the pressure side of theopposite vane 114 situated in the vicinity of saidedge 144′ (FIG. 4 ). - The
oblique margins 166 of theinner platform sectors 130 can bear against one another so as to limit the parasitic deformation and movements of the nozzle sectors in operation. - In order to increase the stiffness of the nozzle of the invention, the
rail sector 134 of eachnozzle sector 112 has at one of its circumferential ends alateral tab 160 bearing axially against the rail sector of an adjacent nozzle sector. Thetab 160 has an orientation that is substantially circumferential and includes a first circumferential end connected to therail sector 134, via its outerradial wall 138. The second circumferential end of thetab 160 includes anaxial bearing face 162 for co-operating with acorresponding face 164 of the outerradial wall 138 of theadjacent rail sector 134, thefaces - In the example shown, the
tab 160 is situated downstream from theradial wall 138 of therail sector 134 and is connected via its first end to a downstream face of said wall. - The bearing face 162 of this tab faces upstream and is designed to bear against a downstream-facing
face 164 of theradial wall 138 of theadjacent rail sector 134. - In a variant, the
tab 160 is situated upstream from theradial wall 138 of the rail sector and is connected via one end to an upstream face of said wall, the bearingface 162 of said tab facing downstream and co-operating with an upstream-facingface 164 of the radial wall of theadjacent rail sector 134. - The
rail sector 134 in eachnozzle sector 112 may be made as a single casting or by machining with at least onelateral bearing tab 160 of the above-described type. In a variant, thelateral tab 160 is a fitting and is fastened to one circumferential ends of each rail sector. Any type of nozzle sector may be fitted with this type of bearing tab.
Claims (13)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0708714 | 2007-12-14 | ||
FR0708714A FR2925107B1 (en) | 2007-12-14 | 2007-12-14 | SECTORIZED DISPENSER FOR A TURBOMACHINE |
Publications (2)
Publication Number | Publication Date |
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US20090155061A1 true US20090155061A1 (en) | 2009-06-18 |
US8147189B2 US8147189B2 (en) | 2012-04-03 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US12/330,630 Active 2030-09-16 US8147189B2 (en) | 2007-12-14 | 2008-12-09 | Sectorized nozzle for a turbomachine |
Country Status (6)
Country | Link |
---|---|
US (1) | US8147189B2 (en) |
EP (1) | EP2071129B1 (en) |
JP (1) | JP5427398B2 (en) |
CA (1) | CA2647057C (en) |
FR (1) | FR2925107B1 (en) |
RU (1) | RU2484261C2 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090129917A1 (en) * | 2007-11-13 | 2009-05-21 | Snecma | Sealing a rotor ring in a turbine stage |
US20090317246A1 (en) * | 2006-06-30 | 2009-12-24 | Fischer Advanced Composite Components Ag | Guide Vane Arrangement for a Driving Mechanism |
US9840917B2 (en) | 2011-12-13 | 2017-12-12 | United Technologies Corporation | Stator vane shroud having an offset |
US10830079B2 (en) | 2017-10-31 | 2020-11-10 | Safran Aircraft Engines | Detachable anti-wear cap for rectifier sector |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2953252B1 (en) * | 2009-11-30 | 2012-11-02 | Snecma | DISTRIBUTOR SECTOR FOR A TURBOMACHINE |
US8905711B2 (en) | 2011-05-26 | 2014-12-09 | United Technologies Corporation | Ceramic matrix composite vane structures for a gas turbine engine turbine |
FR2993002B1 (en) * | 2012-07-09 | 2016-03-18 | Snecma | DISPENSER COMPRISING MEANS FOR MAINTAINING, AND TURBOMACHINE |
FR3041374B1 (en) * | 2015-09-17 | 2020-05-22 | Safran Aircraft Engines | DISTRIBUTOR SECTOR FOR A TURBOMACHINE WITH DIFFERENTIALLY COOLED VANES |
US11359502B2 (en) * | 2020-02-18 | 2022-06-14 | General Electric Company | Nozzle with slash face(s) with swept surfaces with joining line aligned with stiffening member |
US11492917B2 (en) | 2020-02-18 | 2022-11-08 | General Electric Company | Nozzle with slash face(s) with swept surfaces joining at arc with peak aligned with stiffening member |
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US4142827A (en) * | 1976-06-15 | 1979-03-06 | Nuovo Pignone S.P.A. | System for locking the blades in position on the stator case of an axial compressor |
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US20110044798A1 (en) * | 2008-04-24 | 2011-02-24 | Snecma | Turbine nozzle for a turbomachine |
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US4126405A (en) * | 1976-12-16 | 1978-11-21 | General Electric Company | Turbine nozzle |
US4986737A (en) * | 1988-12-29 | 1991-01-22 | General Electric Company | Damped gas turbine engine airfoil row |
DE4017861A1 (en) * | 1990-06-02 | 1991-12-05 | Mtu Muenchen Gmbh | CONDUCTING WREATH FOR A GAS TURBINE |
US5249920A (en) * | 1992-07-09 | 1993-10-05 | General Electric Company | Turbine nozzle seal arrangement |
US5634766A (en) * | 1994-08-23 | 1997-06-03 | General Electric Co. | Turbine stator vane segments having combined air and steam cooling circuits |
FR2728015B1 (en) * | 1994-12-07 | 1997-01-17 | Snecma | SECTORIZED MONOBLOCK DISTRIBUTOR OF A TURBOMACHINE TURBINE STATOR |
RU2171380C2 (en) * | 1999-04-27 | 2001-07-27 | Открытое акционерное общество "Авиадвигатель" | Nozzle block of turbine |
US6893217B2 (en) * | 2002-12-20 | 2005-05-17 | General Electric Company | Methods and apparatus for assembling gas turbine nozzles |
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2007
- 2007-12-14 FR FR0708714A patent/FR2925107B1/en active Active
-
2008
- 2008-10-29 EP EP08167794.0A patent/EP2071129B1/en active Active
- 2008-12-09 US US12/330,630 patent/US8147189B2/en active Active
- 2008-12-10 CA CA2647057A patent/CA2647057C/en active Active
- 2008-12-11 JP JP2008315279A patent/JP5427398B2/en active Active
- 2008-12-12 RU RU2008149160/06A patent/RU2484261C2/en active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US4142827A (en) * | 1976-06-15 | 1979-03-06 | Nuovo Pignone S.P.A. | System for locking the blades in position on the stator case of an axial compressor |
US4285633A (en) * | 1979-10-26 | 1981-08-25 | The United States Of America As Represented By The Secretary Of The Air Force | Broad spectrum vibration damper assembly fixed stator vanes of axial flow compressor |
US20110044798A1 (en) * | 2008-04-24 | 2011-02-24 | Snecma | Turbine nozzle for a turbomachine |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090317246A1 (en) * | 2006-06-30 | 2009-12-24 | Fischer Advanced Composite Components Ag | Guide Vane Arrangement for a Driving Mechanism |
US8297934B2 (en) * | 2006-06-30 | 2012-10-30 | Facc Ag | Guide vane arrangement for a driving mechanism |
US20090129917A1 (en) * | 2007-11-13 | 2009-05-21 | Snecma | Sealing a rotor ring in a turbine stage |
US8100644B2 (en) * | 2007-11-13 | 2012-01-24 | Snecma | Sealing a rotor ring in a turbine stage |
US9840917B2 (en) | 2011-12-13 | 2017-12-12 | United Technologies Corporation | Stator vane shroud having an offset |
US10830079B2 (en) | 2017-10-31 | 2020-11-10 | Safran Aircraft Engines | Detachable anti-wear cap for rectifier sector |
Also Published As
Publication number | Publication date |
---|---|
US8147189B2 (en) | 2012-04-03 |
EP2071129A1 (en) | 2009-06-17 |
CA2647057C (en) | 2015-08-18 |
EP2071129B1 (en) | 2017-05-31 |
CA2647057A1 (en) | 2009-06-14 |
JP2009144718A (en) | 2009-07-02 |
FR2925107B1 (en) | 2010-01-22 |
JP5427398B2 (en) | 2014-02-26 |
RU2484261C2 (en) | 2013-06-10 |
RU2008149160A (en) | 2010-06-20 |
FR2925107A1 (en) | 2009-06-19 |
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